Double-wing embedded flight attitude transformation logistics unmanned aerial vehicle

Abstract

The invention discloses a double-wing embedded logistics unmanned aerial vehicle capable of changing flight attitudes. The unmanned aerial vehicle comprises a box body group, a main wing group and an auxiliary wing group, and an empennage group comprises an engine group embedded in a main wing and the like. The problems of tedious production process, high manufacturing cost and the like are solved through injection molding / or 3D printing processing; the energy-saving effect during cruising flight is achieved through attitude conversion from takeoff to lift-off to cruising flight, namely buoyancy force or lift force generated by the main and auxiliary wings including empennages which are unfolded under windward flight. The logistics distribution unmanned aerial vehicle lifts off like a helicopter when taking off in a static view box body, and flies like an aircraft with windward buoyancy / lift force when cruising and flying. In a word, the production cost is reduced through an injection molding / or 3D printing processing mode; long distance and long endurance time of cruising flight are brought through conversion of flight attitude; therefore, the system is very suitable for logistics distribution operation with video transmission, and opportunities are brought to popularization and use.

Description

Technical Field

[0001] The present invention relates to the technical fields of injection molding / or 3D printing manufacturing and unmanned aerial vehicle technology, and particularly relates to a logistics unmanned aerial vehicle with a double-wing embedded flight attitude transformation. Background Art

[0002] With the continuous improvement of China's material conditions, the extensive use of Beidou navigation technology, and the prevalence of 5G mobile phones today; with the help of Beidou navigation and 5G information transmission including video APP transmission, etc., it has become possible for unmanned aerial vehicles to be used in urban logistics and express delivery; after all, the speed, convenience, and timeliness have attracted much attention. However, when a helicopter is flying, all loads need to be borne by the engine (the power battery is also part of the load), and it works as a lifting and carrying method, so the efficiency is not high. Moreover, the unmanned aerial vehicle needs to be charged or have its battery replaced from time to time, making it difficult to meet people's demands for long-distance flight. If the unmanned aerial vehicle is extended to fly with wings, due to the clamping of flight buoyancy / or lift, like an airplane in flight, the energy-saving effect is greatly improved; it also makes it possible to achieve the flight distance and hovering ability of the unmanned aerial vehicle for logistics and express delivery, that is to say, this will surely bring about the possibility of extensive use.

[0003] Imagine that if the aircraft uses the helicopter method, that is, it takes off under very low site requirements; then when it reaches the cruising flight altitude, it is converted to have a wingspan - that is, it flies like an airplane; that is, relying on the buoyancy / or lift generated by the headwind, the efficiency can be doubled; moreover, with the support of 5G communication and Beidou navigation technology, it is completely possible to develop an unmanned aerial vehicle with a variable battery-driven driving state that meets the needs of logistics distribution. Summary of the Invention

[0004] In view of the above, the purpose of the present invention is to provide "A Logistics Unmanned Aerial Vehicle with a Double-Wing Embedded Flight Attitude Transformation". Through the flight attitude conversion of the unmanned aerial vehicle, the air buoyancy / or lift in the forward direction obtained by expanding the projection area of the double wings - that is, the main and auxiliary wings, is used to achieve the cruise ability that meets the timeliness. Further, for the flight attitude conversion mechanism and electronics, it is made based on injection molding / 3D printing technology to meet the characteristics of innovation and optimization, that is, under the condition that the device has a certain structural strength, performance, and appearance, the purpose of weight reduction is achieved to the greatest extent. Further, it is formed in one piece by injection molding / or 3D printing technology, significantly reducing its production process and processing difficulty, and controlling the production cost. Further, in order to reduce the headwind resistance, the organic integration of the box body with the attitude conversion mechanism and the motor makes the body structure of the unmanned aerial vehicle compact. Further, with the double-wing expansion method, the projection area of the wings (including the tail wing) is expanded. After the flight attitude is converted, the efficiency is higher and it is simple and reliable. Further, that is to say, it well solves the physical indicators in terms of reliability, stability, installation, and maintenance, etc.

[0005] To achieve the above objectives, the present invention provides a bi-wing embedded flight attitude change logistics UAV, which is characterized by comprising:

[0006] The box assembly, as the basic component, is used to achieve flight attitude conversion after takeoff to complete logistics delivery;

[0007] The main and auxiliary wing groups are hinged to the hinge seats on the vertical panels on both sides of the box body, and are used for the conversion of flight attitude, including the expansion of the projected area when the main and auxiliary wing groups are deployed, like the wings of an airplane, to achieve windward buoyancy and / or lift enhancement;

[0008] The tail assembly is hinged to the rear crossbar hinge seat on the box body and is used for flight attitude stabilization and adjustment. Like the tail of an airplane, it completes level and turning control, including the expansion of the projected area, which is conducive to buoyancy and / or lift enhancement;

[0009] The twin engines, embedded in the main wings, are used for attitude conversion and propulsion of the drone from vertical takeoff to cruising flight.

[0010] Preferably, the flight attitude conversion drone is characterized in that the box group includes:

[0011] The upper and lower sides of the vertical plates of the box body are provided with tubular dividing flanges for inserting the main and auxiliary wing attitude control motors into the holes, which synchronously and / or asynchronously drive the main and auxiliary wings to transform between horizontal and vertical positions to achieve the transformation from takeoff to flight attitude; and

[0012] There is a built-in tail attitude control motor embedded in the rear horizontal bar, which is used to drive each tail to transform between super horizontal and vertical, to achieve the height and azimuth adjustment in the air position when taking off to the flight attitude, and also includes the adjustment of the center of mass during vertical takeoff.

[0013] Preferably, the flight attitude conversion drone is characterized in that the box group further includes:

[0014] There is a cover on the cross bar of the box group, and the lower space is used to effectively install the lithium battery pack, flight control circuit, attitude sensing circuit including altitude and azimuth, Beidou navigation signal receiving circuit, 5G signal input and processing circuit, remote control circuit, video transmission circuit, etc.

[0015] Preferably, the flight attitude conversion drone is characterized in that the box group further includes:

[0016] There is a flap design at the front of the box group, which uses a touch-button method to complete the loading and extraction of express items.

[0017] Preferably, the flight attitude conversion drone is characterized in that the box group further includes:

[0018] When the main wing (including the auxiliary wing) is deployed, due to the combination of the two engines embedded in the main wing and gravity, there will be a forward tilting moment on the UAV in the forward direction, which will naturally form a level flight state of the UAV like an airplane, that is, the timely conversion of the flight attitude is completed.

[0019] A dual-wing embedded flight attitude transformation logistics UAV provided by the present invention realizes lightweight through the optimization of various components of the device, including modular design, especially the main components are made by injection molding / or 3D printing process. Further, the attitude transformation motor of the UAV is embedded in the box body, which fully demonstrates the simple structure, reduces the process difficulty and manufacturing cost, and is easy to inspect and maintain. Obviously, the UAV has low cost, guaranteed structural strength, simple process, easy to implement, and can be mass-produced. Most importantly, it has good adaptability and practicability, which is convenient to promote the popularization and application of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Through the following description of the embodiments of the present invention with reference to the drawings, the above and other objects, features and advantages of the present invention will become clearer. In the drawings:

[0021] Figure 1 It is a schematic diagram of the equipment of the flight attitude conversion UAV during cruising in the embodiment of the present invention;

[0022] Figure 2 It is a schematic diagram of the equipment of the flight attitude conversion UAV during vertical takeoff in the embodiment of the present invention;

[0023] Figure 3 It is a schematic diagram of the box body group equipment of the flight attitude conversion UAV in the embodiment of the present invention;

[0024] Figure 4 It is a schematic diagram of the main and auxiliary wing structures of the flight attitude conversion UAV in the embodiment of the present invention;

[0025] Figure 5 It is a schematic diagram of the tail wing equipment of the flight attitude conversion UAV in the embodiment of the present invention;

[0026] Figure 6 It is a schematic diagram of the equipment of the flight attitude conversion UAV during cruising in the second embodiment of the present invention;

[0027] Figure 7 It is a schematic diagram of the equipment of the flight attitude conversion UAV during vertical takeoff in the second embodiment of the present invention;

[0028] Figure 8 It is a schematic diagram of the equipment of the flight attitude conversion UAV during cruising in the third embodiment of the present invention;

[0029] Figure 9This is a schematic diagram of the equipment when the flight attitude conversion unmanned aerial vehicle (UAV) of the third embodiment of the present invention takes off vertically. Specific implementation scheme

[0030] The various embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. In each of the drawings, the same elements are denoted by the same or similar reference numerals. For the sake of clarity, the various parts in the drawings are drawn as much as possible to scale, for example, drawn to scale based on the dimensions in the width and height directions of the box body. In addition, some well-known parts may not be shown in the figures.

[0031] The following combines the accompanying drawings and embodiments to further describe in detail the specific implementation manners of the present invention. Many specific details of the present invention are described below, such as the structure, materials, dimensions, processing techniques, and technologies of components, in order to understand the present invention more clearly. However, as those skilled in the art can understand, the present invention can be implemented without following these specific details.

[0032] Figure 1 This is a schematic diagram of the equipment when the flight attitude conversion UAV of the embodiment of the present invention is cruising; in the figure, the UAV includes: a box body group 1, a main wing group 2, a sub-wing group 3, a tail wing group 4, an attitude control motor 5 (including the control of the main wing group, the sub-wing group, and the tail wing group), two engine groups 6, a flip cover (bolt partition shape) 7, an overall crossbeam body 8, and a camera 9.

[0033] The box body 1 is made by injection molding / or 3D printing process and is used as the main component, which is placed at the central position; when viewed from the front, the four corners of the side vertical plates of the box body group form longitudinal barrel-shaped columnar dividing flanges (see Figure 3) for forming a hinge seat structure to achieve the articulation of the main and auxiliary wings 2 and 3 made by injection molding / or 3D printing, so as to complete the unfolding transformation during flight, that is, to achieve low-power flight like an airplane; among them, in the front flange holes on both sides, a deceleration control motor 5 with a long axis of the attitude of the main and auxiliary wings and a plane is inserted with glue (the attitude control motors are collectively referred to as 5 in the figure), which is used to complete the linkage and support of the main and auxiliary wings (including the planar connection in the flange square holes of the main and auxiliary wings), and complete the attitude control process of the main and auxiliary wings from drooping at takeoff to unfolding during flight. In the upper cross bar on the back, there are also transverse barrel-shaped columnar partitions and flanges to form a hinge seat structure for the articulation of the tail machine 4 made by injection molding / or 3D printing, so as to complete the real-time adjustment of horizontal and steering after attitude conversion; in the flange holes on both sides of the rear end, a deceleration control motor 5 with a long axis of the attitude of the tail wing and a plane is inserted with glue (the attitude control motors are collectively referred to as 5 in the figure) to complete the linkage and support of the tail wing (including the planar connection in the flange square holes of the tail wing), and realize the attitude control of the tail wing from drooping at takeoff to unfolding during flight; at the same time, with the addition of the tail wing, the projected area has been expanded, that is, in the case of having a duct, it is also very helpful for the buoyancy / or lift of the UAV during low-speed flight. There are flange structures on the main wings on both sides of the box body, and an engine drive motor is inserted with glue into the holes to form the drive of the UAV. There is a cover plate arranged on the upper part, and the internal space can be used for the installation of a power supply / circuit box (see Figure 3 ) to integrate the lithium battery, flight control circuit, attitude sensing circuit including altitude and direction, etc., 5G or Beidou positioning circuit, camera control and other circuits.

[0034] According to the box body group structure provided by the above embodiment of the present invention, as a basic component, it is formed by injection molding / or 3D printing process in one step, with simple process and guaranteed structural strength; at the same time, the attitude control motor is glued and embedded in the flange hole, presenting an integrated structure, which also makes the structure simple and reliable.

[0035] Figure 2 It is a schematic diagram of the equipment of the UAV with flight attitude conversion during vertical takeoff according to the embodiment of the present invention; in the vertical takeoff attitude, it consists of: box body 1, main wing group 2, auxiliary wing group 3, tail wing group 4, attitude conversion motor 5 (the attitude control motors are collectively referred to as 5), two engine groups 6, flip door 7, overall cross beam body 8, camera 9.

[0036] As can be seen from the figure, before takeoff, the main and auxiliary wings and the tail wing are all in a drooping and contracted attitude, with a body shape like a box, reducing the projected area, which is convenient for reducing the resistance and energy consumption during vertical takeoff. In contrast Figure 1 , when the main and auxiliary wings 2 and 3 are unfolded, a projected area with expanded wings (including the tail wing 4) is formed, which is convenient for forming a larger windward buoyancy / lift, greatly reducing the engine drive energy consumption, and ensuring the long-distance flight ability and longer holding time.

[0037] Figure 3Schematic diagram of the box set equipment for the flight attitude conversion unmanned aerial vehicle according to the embodiment of the present invention; as shown in the figure, the box set can be divided into upper and lower parts, which are completed by thin-wall injection molding / or 3D printing; at the upper part of the box 1, there are two side vertical plates forming four-corner longitudinal barrel-shaped columnar dividing flanges, which are used to form a hinge seat structure to realize the hinging of the main and auxiliary wings made by injection molding / or 3D printing process, so as to complete the unfolding transformation during takeoff to cruise flight, that is, to generate buoyancy / or lift in the case of facing the wind - that is, in the shape of an airplane, to form low-power flight; among them, in the oncoming flange hole, a rectangular shaft reduction motor 5 for the state transformation of the main and auxiliary wings is inserted with glue, and a greased bushing is inserted between the flanges to form a support, so as to form the linkage of the main and auxiliary wings (including the planar connection of the flange square holes of the main and auxiliary wings), and realize the attitude control of the drooping of the main and auxiliary wings at takeoff to the unfolding during flight. There are transverse barrel-shaped columnar dividing flanges on the back to form a hinge seat structure for the hinging of the tail wing group completed by injection molding / or 3D printing process, so as to complete the timely adjustment of horizontal and steering after the state attitude transformation; among them, a long shaft for the tail wing attitude with glue and a planar control motor 5 (all state control motors are collectively called 5) are provided, and a greased sleeve is inserted into the flange hole of the box to complete the linkage of the tail wing (including the planar connection of the flange square holes of the tail wing), so as to realize the attitude control of the drooping of the tail wing at takeoff to the upward tilt during flight; at the same time, the addition of the tail wing expands the projected area, that is, in the case of having an air duct, it is also very helpful for the buoyancy / or lift of the unmanned aerial vehicle during cruise flight; the internal space of the overall crossbeam body 8 at the upper part of the box is used for installing the lithium battery and the control circuit box.

[0038] According to the box set structure provided by the above embodiment of the present invention, as a basic component, it is formed by one-time injection molding / or 3D printing process, with simple process and guaranteed structural strength; at the same time, the attitude control motor is inserted into the flange hole with glue, presenting an integrated structure, which also makes the structure simple and reliable. At the same time, the integrated design of the battery / circuit box packaging also shows a simple structure.

[0039] Figure 4 Schematic diagram of the main and auxiliary wing structure of the flight attitude conversion unmanned aerial vehicle according to the embodiment of the present invention; contrast Figure 1 and 2The main and auxiliary wings are placed on either side of the housing assembly, corresponding to each other, and are manufactured using injection molding or 3D printing. Splitting flanges at one end of the front and rear components form a hinge structure that articulates with the hinge seat in the housing, enabling attitude control during cruise. Square holes in the flanges accommodate the long-shaft square-shaped wing attitude control motor 5 with a speed reducer, forming a connection with the square holes in the flanges. Greased sleeves are placed in the alternate flange holes between the hinge seats on the housing to provide lubrication and support for the long shaft, thereby driving synchronous rotation. Pre-defined arc-shaped notches are provided between the flanges to facilitate smooth, fixed-axis rotation with the hinge seat in the housing. The wings are designed as thin, cantilever beams to reduce cross-sectional drag. Corner structures at the lower ends of the two components, resembling aircraft tail fins, provide flow stabilization, aiding wind resistance and stable flight during cruise. A flange in the center of the main wing accommodates the engine drive motor 6 and its additional blades, completing the engine drive.

[0040] The main and ailerons, as hinged rotating components, provided in the above-described embodiments of the present invention are manufactured using injection molding or 3D printing, resulting in simple and convenient manufacturing. The expanded projected area of the main and ailerons when deployed is the fundamental guarantee for generating lift and / or buoyancy during cruising.

[0041] Figure 5 This is a schematic diagram of the tail structure of a UAV with flight attitude conversion according to an embodiment of the present invention; as shown in the figure, the tail 4 is the right-left part, placed at the top corner of the upper rear side of the box assembly, and is made by injection molding / or 3D printing. There is a flange on the upper part, which is used for hinge connection with the box hinge seat to form attitude conversion during cruising. There is a square hole in the middle of the flange corresponding to the insertion of the long axis 5 of the tail attitude control motor (all state control motors are collectively referred to as 5), forming a plane connection; and greased sleeves are placed in the alternate flange holes of the hinge seat on the box to form a long axis for necessary support (see Figure 3 ) to achieve synchronous rotation. Pre-defined curved notches on the flange allow for smooth, unimpeded rotation when mated with the connector in the housing. A curved edge at the bottom enhances overflow during cruising, mimicking vortices caused by the lower cross-section. Angular vertical surfaces on both sides act like an aircraft tail in cruising mode, providing excellent flow stabilization and wind resistance.

[0042] The tail fins provided in the flight attitude switching drone according to the above embodiment of the present invention are used as rotating parts and are manufactured using injection molding or 3D printing processes, which are simple and easy to implement. The two tail fins can rotate asynchronously to achieve horizontal flight during cruising and attitude switching during turning.

[0043] Figure 6 This is a schematic diagram of the equipment for the second embodiment of the present invention when the flight attitude conversion drone is cruising; Figure 1, a third engine is added to the front middle part of the overall crossbeam body; at the same time, the installation positions of the first and second engines are shifted outward to the edges of the main wings, and it is driven by three engines; for the rest, it is the same as Figure 1 and will not be described here again.

[0044] Figure 7 is a schematic diagram of the equipment of the unmanned aerial vehicle for flight attitude conversion in the second embodiment of the present invention during vertical takeoff; it shows the state before takeoff with three engines; compared with Figure 2 and will not be described here again.

[0045] Figure 8 is a schematic diagram of the equipment of the unmanned aerial vehicle for flight attitude conversion in the third embodiment of the present invention during cruising; compared with Figure 1 , engines are added on both sides of the main engine, that is, it shows the state driven by four engines; for the rest, it is the same as Figure 1 and will not be described here again.

[0046] Figure 9 is a schematic diagram of the equipment of the unmanned aerial vehicle for flight attitude conversion in the third embodiment of the present invention during vertical takeoff; it shows the state before takeoff with four engines; compared with Figure 2 and will not be described here again.

[0047] In summary, an embodiment of the present invention, a two-wing embedded unmanned aerial vehicle for flight attitude transformation in logistics, has obvious structural contraction characteristics during takeoff and double-wing deployment characteristics during flight attitude, which greatly reduces the energy consumption from takeoff to cruising flight; especially, it is greatly enhanced in terms of cruising ability. The main components are prepared by injection molding / or 3D printing process, and good optimization is achieved including lightweight structure, which makes the structure concise, brings convenience to the overall manufacturing, and also well controls the cost.

[0048] The attitude control motor embedded in the box body brings good organic coordination to the control of the engine, main wings, auxiliary wings, and tail wings, and reduces the volume; at the same time, the separate control of the engine, main and auxiliary wings, and tail wings can strengthen the good control of the flight attitude. In short, the unmanned aerial vehicle for flight attitude conversion in logistics delivery with double engines and double wings made of injection molding / or 3D printing components can be drawn according to the actual size and can be refined to guide production; it can also play a role in promoting the popularization and application of unmanned aerial vehicle technology.

[0049] The above are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, the present invention can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A two-engine main-wing embedded double-wing aluminum inspection UAV, characterized in that Including: A box body group, as a basic component, is used to realize the flight attitude conversion after taking off into the air to complete logistics delivery; A main and auxiliary wing group, which is hinged to the hinge seats on the two side vertical plates of the box body, is used for the conversion of flight attitude, including the expansion of the projected area when the main and auxiliary wing groups are unfolded. Like an airplane wing, it realizes the improvement of windward buoyancy / lift; A tail wing group, which is hinged to the hinge seat of the rear cross bar on the box body, is used for flight attitude stabilization and adjustment. Like an airplane tail wing, it completes horizontal and turning control and also includes the expansion of the projected area, which is beneficial to the improvement of buoyancy / lift; Twin engines, which are inlaid with the main wing, are used for the attitude conversion and drive of the UAV from vertical takeoff to cruise flight.

2. The flight attitude conversion unmanned aerial vehicle according to claim 1, wherein The box body group includes: There are tubular dividing flanges on the upper and lower parts of the two side vertical plates of the box body, which are used to insert the main and auxiliary wing attitude control motors into the holes to drive the main and auxiliary wings to transform between horizontal and vertical synchronously / non-synchronously, realizing the takeoff into the air to the flight attitude transformation; and There is an embedded tail wing attitude control motor in the rear cross bar, which is used to drive the respective tail wings to transform between super horizontal and vertical, realizing the adjustment of the height and azimuth of the in-air position during the takeoff to flight attitude transformation, including the adjustment of the center of mass during vertical takeoff.

3. The flight attitude conversion unmanned aerial vehicle according to claim 2, characterized in that The box body group also includes: There is a cover plate on the cross bar body of the box body group, and the lower space is used to effectively install the lithium battery pack, flight control circuit, attitude sensing circuit including height and azimuth, Beidou navigation signal receiving circuit, 5G signal input and processing circuit, remote control circuit, video transmission circuit, etc.

4. The flight attitude conversion drone according to claim 2, wherein The box body group also includes: There is a flip door design at the front of the box body group, which uses a catch to complete the loading and extraction of express items.

5. The flight attitude conversion unmanned aerial vehicle according to claim 2, wherein The box body group also includes: When the main wing (including the auxiliary wing) is unfolded, due to the synthesis of the two engines inlaid on the main wing and gravity, there will be a forward tilting torque on the UAV in the forward direction. In this way, it will naturally form a level flight state of the UAV like an airplane, that is, the timely conversion of the flight attitude is completed.

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